US7316539B2 - Vane assembly with metal trailing edge segment - Google Patents
Vane assembly with metal trailing edge segment Download PDFInfo
- Publication number
- US7316539B2 US7316539B2 US11/101,255 US10125505A US7316539B2 US 7316539 B2 US7316539 B2 US 7316539B2 US 10125505 A US10125505 A US 10125505A US 7316539 B2 US7316539 B2 US 7316539B2
- Authority
- US
- United States
- Prior art keywords
- segment
- airfoil
- aft
- insert
- segments
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related, expires
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/301—Cross-sectional characteristics
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
- F05D2240/57—Leaf seals
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/21—Oxide ceramics
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
Definitions
- the forward airfoil segment 12 can be generally airfoil-shaped. It will be understood that embodiments of the invention are not limited to any particular airfoil conformation.
- One end of the forward segment 12 can define the leading edge 16 of the vane assembly 10 .
- the opposite end of the forward segment 12 can provide an interface surface 18 .
- the interface surface 18 can have any of a number of configurations. In one embodiment, the interface surface 18 can be substantially flat. In another embodiment, the interface surface 18 can be rounded.
Abstract
Description
Claims (7)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/101,255 US7316539B2 (en) | 2005-04-07 | 2005-04-07 | Vane assembly with metal trailing edge segment |
US11/901,551 US7837438B2 (en) | 2005-04-07 | 2007-09-18 | Vane assembly with metal trailing edge segment |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/101,255 US7316539B2 (en) | 2005-04-07 | 2005-04-07 | Vane assembly with metal trailing edge segment |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/901,551 Division US7837438B2 (en) | 2005-04-07 | 2007-09-18 | Vane assembly with metal trailing edge segment |
Publications (2)
Publication Number | Publication Date |
---|---|
US20060226290A1 US20060226290A1 (en) | 2006-10-12 |
US7316539B2 true US7316539B2 (en) | 2008-01-08 |
Family
ID=37082299
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/101,255 Expired - Fee Related US7316539B2 (en) | 2005-04-07 | 2005-04-07 | Vane assembly with metal trailing edge segment |
US11/901,551 Expired - Fee Related US7837438B2 (en) | 2005-04-07 | 2007-09-18 | Vane assembly with metal trailing edge segment |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/901,551 Expired - Fee Related US7837438B2 (en) | 2005-04-07 | 2007-09-18 | Vane assembly with metal trailing edge segment |
Country Status (1)
Country | Link |
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US (2) | US7316539B2 (en) |
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US20100068034A1 (en) * | 2008-09-18 | 2010-03-18 | Schiavo Anthony L | CMC Vane Assembly Apparatus and Method |
US20100080687A1 (en) * | 2008-09-26 | 2010-04-01 | Siemens Power Generation, Inc. | Multiple Piece Turbine Engine Airfoil with a Structural Spar |
US20100172760A1 (en) * | 2009-01-06 | 2010-07-08 | General Electric Company | Non-Integral Turbine Blade Platforms and Systems |
US20100189556A1 (en) * | 2009-01-28 | 2010-07-29 | United Technologies Corporation | Segmented ceramic matrix composite turbine airfoil component |
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US20100322760A1 (en) * | 2009-06-17 | 2010-12-23 | Morrison Jay A | Interlocked CMC Airfoil |
US20110110790A1 (en) * | 2009-11-10 | 2011-05-12 | General Electric Company | Heat shield |
US8347636B2 (en) | 2010-09-24 | 2013-01-08 | General Electric Company | Turbomachine including a ceramic matrix composite (CMC) bridge |
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US20150004000A1 (en) * | 2013-03-04 | 2015-01-01 | Rolls-Royce North American Technologies, Inc | Method for making gas turbine engine ceramic matrix composite airfoil |
US9011087B2 (en) | 2012-03-26 | 2015-04-21 | United Technologies Corporation | Hybrid airfoil for a gas turbine engine |
US20180135423A1 (en) * | 2016-11-17 | 2018-05-17 | General Electric Company | Double impingement slot cap assembly |
US20180230945A1 (en) * | 2015-07-22 | 2018-08-16 | Safran Aircraft Engines | Aircraft comprising a rear fairing propulsion system with inlet stator comprising a blowing function |
US10060272B2 (en) | 2015-01-30 | 2018-08-28 | Rolls-Royce Corporation | Turbine vane with load shield |
US10196910B2 (en) | 2015-01-30 | 2019-02-05 | Rolls-Royce Corporation | Turbine vane with load shield |
US10309226B2 (en) | 2016-11-17 | 2019-06-04 | United Technologies Corporation | Airfoil having panels |
US10309238B2 (en) | 2016-11-17 | 2019-06-04 | United Technologies Corporation | Turbine engine component with geometrically segmented coating section and cooling passage |
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US10428658B2 (en) | 2016-11-17 | 2019-10-01 | United Technologies Corporation | Airfoil with panel fastened to core structure |
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US10436049B2 (en) | 2016-11-17 | 2019-10-08 | United Technologies Corporation | Airfoil with dual profile leading end |
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US10458262B2 (en) | 2016-11-17 | 2019-10-29 | United Technologies Corporation | Airfoil with seal between endwall and airfoil section |
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US20090003988A1 (en) | 2009-01-01 |
US7837438B2 (en) | 2010-11-23 |
US20060226290A1 (en) | 2006-10-12 |
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